WO2004090290A2 - Turbomachine thermique - Google Patents

Turbomachine thermique Download PDF

Info

Publication number
WO2004090290A2
WO2004090290A2 PCT/EP2004/050512 EP2004050512W WO2004090290A2 WO 2004090290 A2 WO2004090290 A2 WO 2004090290A2 EP 2004050512 W EP2004050512 W EP 2004050512W WO 2004090290 A2 WO2004090290 A2 WO 2004090290A2
Authority
WO
WIPO (PCT)
Prior art keywords
abrasive
abrasive layer
blade
rotor
blades
Prior art date
Application number
PCT/EP2004/050512
Other languages
German (de)
English (en)
Other versions
WO2004090290A3 (fr
Inventor
Johnson Nicolas Campino
Matthias Hoebel
Jonas Hurter
Christoph Niederberger
Original Assignee
Alstom Technology Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Alstom Technology Ltd filed Critical Alstom Technology Ltd
Priority to JP2006505554A priority Critical patent/JP2006522894A/ja
Priority to EP04727018A priority patent/EP1613840A2/fr
Publication of WO2004090290A2 publication Critical patent/WO2004090290A2/fr
Publication of WO2004090290A3 publication Critical patent/WO2004090290A3/fr
Priority to US11/249,625 priority patent/US7425115B2/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position

Definitions

  • the invention is based on a thermal turbomachine having a rotor, a stator, an abradable layer located on the stator and at least one row of rotor blades which are arranged around the circumference of the rotor opposite the stator.
  • the guide and rotor blades of gas turbines or compressors are exposed to heavy loads.
  • the rotor blade of the turbomachine is fitted to the stator in such a way that rubbing occurs.
  • a honeycomb structure is attached to the stator of the gas turbine or the compressor, opposite the rotor blade.
  • a compressor with such a honeycomb structure is known for example from US-A-5,520,508. The blades of the compressor work their way into this structure, so that there is a minimal sealing gap between the blades and the honeycomb structure.
  • the honeycomb structure consists of a heat-resistant metal alloy. It is composed of several sheet metal strips, which are bent according to the later shape.
  • the blade tips which are inserted into such an abradable structure, are usually provided with an abrasive layer in order to prevent or at least minimize wear or shortening of the rotor blade.
  • an abrasive layer in order to prevent or at least minimize wear or shortening of the rotor blade.
  • US-A-5,704,759, US-A-4,589,823 and US-A-5,603,603 disclose tur- Bin scoops, which are equipped with abrasive materials at the tip of the scoop.
  • US-B1-6,194,086 discloses an abrasive protective layer in which cubic bomitrides embedded in a matrix are applied to a turbine blade by means of a plasma spray process.
  • abrasive layers with very good cutting properties have a very short lifespan of up to just a few hours.
  • the base material of the blading is usually only suitable to a limited extent in order to work unprotected into the coating on the stator, since this can melt during the rubbing process and can deposit or smear on the stator side. If the blade material has become so deposited, the grinding system is disrupted and the blades are shortened during the rub-in process.
  • approx. 80% of the rub-in depth which results from the rotor blading in the abradable layer of the stator, is achieved in the first hours after a new start-up by the rub-in procedure. After completing the rub-in procedure, the blading on the stator is very rarely streaked and then only with shallow penetration depths.
  • the invention has for its object to provide a thermal turbomachine in which the blades aggressively insert into the stator material with a considerable depth of penetration during commissioning and the rub-in procedure. cut, while the blades then only cut or rub in to a small extent in commercial operation in a long operational phase. This is to ensure that the abrasive material survives less contact with the stator without damage during this time.
  • a first embodiment of the present invention is to provide a number of first rotor blades that are only coated with a first aggressively cutting, abrasive layer.
  • the blades, which are equipped with the first abrasive layer, are longer than all other blades and are therefore the only ones that have to do cutting work when they come into contact with the stator.
  • blades which have only a second, thermally more stable abrasive layer, are distributed over the circumference of the rotor. These blades have a shorter radial length than the first blades, which are equipped with the first abrasive layer, and a greater radial length than unarmored blades. The much larger number of blades, which are distributed over the circumference of the rotor, do not have an abrasive layer. However, these rotor blades are protected by the rotor blades with an abrasive layer to such an extent that an unarmored rotor blade does not come into contact with the stator.
  • first blades with two, a second abrasive and a first abrasive layer on the blade tip.
  • the top abrasive layer is aggressive, but has only a low thermal stability.
  • the lower abrasive layer which appears after the upper abrasive layer wears out, is now less aggressive in its cutting behavior, but thermally much more stable.
  • the blades, which are provided with the first abrasive layer are longer than all other blades and are therefore the only ones that have to do cutting work when they come into contact with the stator. Thus, only the abrasive layer is in contact with the stator during the commissioning of the thermal turbomachine and the associated rub-in procedure.
  • the abrasive layers preferably consist of very hard cubic boron nitrides with a titanium coating, which are embedded in a matrix of filler material.
  • the matrix in which the particles are embedded consists of relatively ductile, well-wetting material.
  • the advantage of these coatings is the combination of the aggressive cutting behavior generated by the hard materials with the toughness gained by the ductile matrix. With the good wetting between the titanium coating and compatible filler, this results in a system that can withstand the strong mechanical loads during the rub-in process.
  • Either a steel alloy similar to the base material or a nickel material with small additions of Bi and S is used as the filler in the coating of compressor blades. Suitable components based on nickel or cobalt can also be used for components from the turbine stage with higher temperatures.
  • FIG. 1 shows a turbine blade according to the invention with an abrasive protective layer at the tip
  • FIG. 2 shows a rotor of a turbomachine according to the invention with a number of moving blades which are arranged opposite a stator
  • FIG. 4 shows a device for coating a turbine blade
  • FIG. 5 shows a control system for the device of FIGS. 4 and 6 shows a compressor blade tip with an abrasive protective layer which is realized by the invention
  • FIG. 7 shows the micrograph of an abrasive coating.
  • the rotor blade 1 shows a rotor blade 1 of a gas turbine, a compressor or another thermal turbomachine.
  • the rotor blade 1 consists of an airfoil 4 with a blade tip 2 and a blade root 3, with which the rotor blade 1 is mounted on a rotor 9.
  • a platform 5 is usually arranged between the airfoil 4 and the airfoil 3, which platform shields the airfoil 3 and thus the rotor 9 from the fluids flowing around the airfoil 4.
  • the blade 1 can be covered with a protective layer 6 made of MCrAIY and additional ceramic material (TBC).
  • An abrasive protective layer 7 is arranged at the tip of this rotor blade 1.
  • Fig. 2 shows a section of a blade row of the thermal turbomachine.
  • the blades 1 are attached to the rotor 9 and arranged opposite the stator 8. According to the invention, a small number of rotor blades 1 of a rotor blade row arranged over the circumference of the rotor 9 are equipped with two different abrasive layers 7 1, 7 2 on the blade tip 2.
  • the top abrasive layer 7 2 with the height x 2 is aggressively outgoing, but has only a low thermal stability.
  • the lower abrasive layer 7 ⁇ with the height xi which appears after wear of the upper abrasive layer 7 2 , is now less aggressive in the cutting behavior, but is, however, much more thermally stable.
  • the qualitative relationship between the quality of the cutting ability Q and the thermal resistance T of the abrasive layers 7 ⁇ , 7 2 is shown schematically in FIG. 3.
  • the blades 1, which are provided with the abrasive layer 7 2 are longer than all other blades 1 and thus the only ones that have to do cutting work when they come into contact with the stator 8.
  • the blades 1, which are provided with the abrasive layer 7 2 are longer than all other blades 1 and thus the only ones that have to do cutting work when they come into contact with the stator 8.
  • only the abrasive layer 7 2 is in contact with the stator 8 during a (new) start-up of the thermal turbomachine and the associated rub-in procedure.
  • this upper, aggressively cutting, but thermally less stable abrasive layer 7 2 wears out.
  • only the lower abrasive layer 7 is in contact with the stator 8 in the following commercial phase of the turbomachine.
  • a simple variant of the present invention consists in using moving blades 1 with three different lengths in one row of blades.
  • a number of first rotor blades 1 are only coated with a first aggressively cutting, abrasive layer 7 2 .
  • the blades 1, which are equipped with the first abrasive layer 7 2 are longer than all other blades 1 and thus the only ones that have to do cutting work when they come into contact with the stator 8.
  • additional blades 1 which exclusively have a lower abrasive layer 7, which have less good cutting properties, but have substantially greater thermal stability, are distributed over the circumference of the rotor 9. As shown in FIG. 2, these blades 1 have a shorter radial length than the first blades 1, which are equipped with the first or upper abrasive layer 7 2 , and a greater radial length than non-armored blades 1.
  • FIGS. 4 and 5 schematically show a device and a method for applying an abrasive layer 7 ⁇ , 7 2 to the tip of a blade 1.
  • Such a method is known for example from DE-C1-198 53 733.
  • the first abrasive layer 7 2 preferably consists of very hard cubic boron nitride (cBN), while the second abrasive layer 7 2 consists of carbides, in particular chromium carbides, each of which is embedded in a matrix of filler material.
  • the matrix in which the particles are embedded consists of relatively ductile, well-wetting material and the wetting of the abrasive particles can be increased by a titanium or nickel coating.
  • the advantage of these coatings is the combination of the aggressive cutting behavior generated by the hard materials with the toughness gained through the ductile matrix. With the good wetting between the titanium coating and compatible filler, this results in a system that can withstand the strong mechanical loads during the rub-in process.
  • Fig. 4 shows a general example of a device for applying a coating 17, which corresponds to the abrasive layer 7 ⁇ , 7 2 , on the blade tip 2 of a moving blade 1.
  • a laser beam 11 is moved over the surface 10 of the moving blade 1 (or the moving blade 1 becomes relative to the laser beam 11), the surface 10 being locally melted.
  • a melt pool 12 is thereby formed.
  • powdery material 13 and a carrier gas 14 are fed to the melt pool 12 by means of a feed nozzle 15 and a nozzle 15a in the form of a jet.
  • the powdery material can be a suitable mixture of abrasive hard material and binder material.
  • An optical signal 18 is continuously recorded by the melt pool 12 and used as properties of the melt pool 12 for determining the temperature, the temperature fluctuations and gradients.
  • the present method is also suitable for the coating of three-dimensional objects.
  • the powder 13 is added to the melt pool 12 concentrically with respect to the cone of the optical signals 18 detected by the melt pool 12.
  • FIG. 5 shows an entire controller 21 for the device of FIG. 4.
  • the information of the optical signal 18 is used in a closed control loop in the controller 21 to process parameters such as laser power, the relative speed between the laser beam 11 and the coating component, the volume flow of the carrier gas 14, the mass flow of the injected powder 13, the distance between the nozzle 15a and the rotor blade 1 and adjust the angle between the nozzle 15a and the blade 1.
  • a regulator 24 is used to regulate the laser power, and a regulator 23 within the regulator 21 is used to regulate the feed nozzle 15.
  • the molten pool 12 then solidifies as a coating.
  • the automatic regulation of the laser power by the controller 21 makes it possible to set a temperature field which is advantageous for achieving the desired microstructure of the coating 17.
  • the optical signal 18 can be used to avoid Marangoni convection in the melt pool 12. This minimizes the risk of defects forming during the solidification of the molten material.
  • High-power lasers such as C0 2 , fiber-coupled Nd-YAG or diode lasers are particularly suitable as an energy source.
  • the laser radiation can be focused on small spots and changed, which allows a very precise control of the energy input into the base material.
  • the controller 24 for the laser power is decoupled from the main process controller 22. This enables the data to be processed faster in real time.
  • the present method uses a concentric feed nozzle 15, a laser 11 and an online monitoring system with real-time process control. With the help of this online monitoring system, optimal process parameters can be set in order to obtain a desired microstructure of the coating 17.
  • the method combines the laser beam and material supply and the monitoring system in a common head.
  • a dichroic mirror 19 the infrared (IR) radiation from the molten pool 12 can be recorded by the same optics that are used for the laser beam.
  • the dichroic mirror 19 transmits the laser beam 11 to the melt pool 12 and is at the same time permeable to the optical signal 18 from the melt pool 12.
  • the optical signal 18 is transmitted from the melt pool 12 to a pyrometer 20 or another detector in order to carry out the online determination of the temperature of the melt pool 12.
  • the optical properties of the monitoring system are selected such that the measurement spot is smaller than the weld pool 12 and is located in the middle of the weld pool.
  • FIG. 6 shows an example of a coated compressor blade tip which was implemented by the described method. It can be seen that the coated component is a thin-walled structure that would deform if excessive heat was introduced, which would result in unacceptable tolerances. This is avoided by the locally very limited action of the laser and the exact power control and the dimensions of the component are changed only minimally.
  • FIG. 7 shows a longitudinal section through an abrasively coated compressor blade tip.
  • the base material of the blade consists of austenitic steel and the approximately 300 ⁇ m thick coating was created by a mixture of Ti-coated cBN hard material particles and NiBSi binder material. In this case, it is an example in which only a single coating was applied.
  • the cBN hard material particles can be recognized as blocky structures in the upper half of the coating. They are completely encased in binder material, which demonstrates the good wetting of the hard material particles.
  • Fig. 7 shows that with good process control, e.g. by the controller already described in FIG. 5, a crack and pore-free structure with excellent connection to the base material can be realized.
  • the optical signal 18 used for power control is generated from the center and edge areas of the fusible zone by means of a fiber-optic image guide or a CCD camera. of the recorded.
  • the CCD camera used as a detector is equipped with suitable optical filters. This information is then used to determine the temperature at one or at several points in the center or edge region of the melting bath 12.
  • the cone of the detected optical signal 18 can be arranged concentrically to the focused laser beam. This symmetrical arrangement guarantees that the interaction processes between laser and powder 13 are identical for all directions of movement. This is particularly advantageous when machining complex-shaped components, since the constant interaction processes ensure consistently good machining quality.
  • the optical signal 18 emitted by the melt pool 12 is used for quality control: the analysis of the measured values made it possible to optimize the process parameters in such a way that a desired microstructure of the coating results.
  • the signals can also be recorded for documentation purposes and to ensure consistently good product quality.
  • Customized, commercially available software tools eg LabView RT
  • software tools eg LabView RT
  • control times of ⁇ 10ms are possible.
  • complex PID regulations can be implemented for the control system with parameters that are specifically tailored to the respective temperature range.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une turbomachine thermique comprenant au moins une série de pales (1). Au moins une première pale (1) présente une longueur radiale supérieure à celle des autres, et la pointe (2) de cette pale est pourvue d'une première couche abrasive (72). Au moins une autre pale (1) présente une longueur radiale inférieure à celle de ladite première pale (1) et la pointe (2) de cette autre pale est pourvue d'une deuxième couche abrasive (71). Ladite première couche abrasive (72) présente un meilleur pouvoir tranchant et une thermostabilité plus faible que ladite deuxième couche abrasive (71). Lors de la mise en marche de la turbomachine thermique, la première couche abrasive (72) se trouve en contact avec la couche abradable du stator (8), et lors du fonctionnement en continu de ladite turbomachine thermique, c'est la deuxième couche abrasive (71) qui se trouve en contact avec la couche abradable du stator (8).
PCT/EP2004/050512 2003-04-14 2004-04-13 Turbomachine thermique WO2004090290A2 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
JP2006505554A JP2006522894A (ja) 2003-04-14 2004-04-13 熱的なターボ機械
EP04727018A EP1613840A2 (fr) 2003-04-14 2004-04-13 Turbomachine thermique
US11/249,625 US7425115B2 (en) 2003-04-14 2005-10-14 Thermal turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH20030674/03 2003-04-14
CH00674/03A CH696854A5 (de) 2003-04-14 2003-04-14 Thermische Turbomaschine.

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US11/249,625 Continuation US7425115B2 (en) 2003-04-14 2005-10-14 Thermal turbomachine

Publications (2)

Publication Number Publication Date
WO2004090290A2 true WO2004090290A2 (fr) 2004-10-21
WO2004090290A3 WO2004090290A3 (fr) 2004-11-18

Family

ID=33136761

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2004/050512 WO2004090290A2 (fr) 2003-04-14 2004-04-13 Turbomachine thermique

Country Status (5)

Country Link
US (1) US7425115B2 (fr)
EP (1) EP1613840A2 (fr)
JP (1) JP2006522894A (fr)
CH (1) CH696854A5 (fr)
WO (1) WO2004090290A2 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1609953A1 (fr) * 2004-06-24 2005-12-28 BorgWarner Inc. Méthode d'assemblage pour une turbomachine
EP2573326A1 (fr) * 2011-09-23 2013-03-27 United Technologies Corporation Agencement de joint d'extrémité d'aube
EP3318719A1 (fr) * 2016-11-07 2018-05-09 United Technologies Corporation Composant de turbomachine revêtu
DE102019116746A1 (de) * 2019-06-20 2020-12-24 Rolls-Royce Deutschland Ltd & Co Kg Rotorbaugruppe und Herstellungsverfahren

Families Citing this family (10)

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Publication number Priority date Publication date Assignee Title
GB0911500D0 (en) * 2009-07-03 2009-08-12 Rolls Royce Plc Rotor blade over-tip leakage control
EP2317078B2 (fr) * 2009-11-02 2021-09-01 Ansaldo Energia IP UK Limited Aube de turbine abrasive monocristalline
US20150093237A1 (en) * 2013-09-30 2015-04-02 General Electric Company Ceramic matrix composite component, turbine system and fabrication process
US20150315090A1 (en) * 2014-05-01 2015-11-05 Siemens Energy, Inc. Laser glazing using hollow objects for shrinkage compliance
US10132185B2 (en) 2014-11-07 2018-11-20 Rolls-Royce Corporation Additive process for an abradable blade track used in a gas turbine engine
US11078588B2 (en) 2017-01-09 2021-08-03 Raytheon Technologies Corporation Pulse plated abrasive grit
US10900371B2 (en) 2017-07-27 2021-01-26 Rolls-Royce North American Technologies, Inc. Abradable coatings for high-performance systems
US10858950B2 (en) 2017-07-27 2020-12-08 Rolls-Royce North America Technologies, Inc. Multilayer abradable coatings for high-performance systems
US11299993B2 (en) * 2019-10-28 2022-04-12 Honeywell International Inc. Rotor assembly for in-machine grinding of shroud member and methods of using the same
US20230235680A1 (en) * 2022-01-26 2023-07-27 General Electric Company Non-uniform turbomachinery blade tips for frequency tuning

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US4390320A (en) * 1980-05-01 1983-06-28 General Electric Company Tip cap for a rotor blade and method of replacement
DE3401742A1 (de) * 1984-01-19 1985-07-25 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Rotor einer axialstroemungsmaschine
GB2225388A (en) * 1988-10-01 1990-05-30 Rolls Royce Plc Rotor blade tip clearance setting in gas turbine engines
US5264011A (en) * 1992-09-08 1993-11-23 General Motors Corporation Abrasive blade tips for cast single crystal gas turbine blades
DE4439726A1 (de) * 1994-11-09 1996-05-15 Siemens Ag Laufrad für eine Strömungsmaschine
US5997248A (en) * 1998-12-03 1999-12-07 Sulzer Metco (Us) Inc. Silicon carbide composition for turbine blade tips
US20010014403A1 (en) * 1997-08-12 2001-08-16 Lawrence Evans Brown Method and apparatus for making components by direct laser processing

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US5603603A (en) 1993-12-08 1997-02-18 United Technologies Corporation Abrasive blade tip
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US5932356A (en) * 1996-03-21 1999-08-03 United Technologies Corporation Abrasive/abradable gas path seal system
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Publication number Priority date Publication date Assignee Title
US3199836A (en) * 1964-05-04 1965-08-10 Gen Electric Axial flow turbo-machine blade with abrasive tip
US4390320A (en) * 1980-05-01 1983-06-28 General Electric Company Tip cap for a rotor blade and method of replacement
DE3401742A1 (de) * 1984-01-19 1985-07-25 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Rotor einer axialstroemungsmaschine
GB2225388A (en) * 1988-10-01 1990-05-30 Rolls Royce Plc Rotor blade tip clearance setting in gas turbine engines
US5264011A (en) * 1992-09-08 1993-11-23 General Motors Corporation Abrasive blade tips for cast single crystal gas turbine blades
DE4439726A1 (de) * 1994-11-09 1996-05-15 Siemens Ag Laufrad für eine Strömungsmaschine
US20010014403A1 (en) * 1997-08-12 2001-08-16 Lawrence Evans Brown Method and apparatus for making components by direct laser processing
US5997248A (en) * 1998-12-03 1999-12-07 Sulzer Metco (Us) Inc. Silicon carbide composition for turbine blade tips

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1609953A1 (fr) * 2004-06-24 2005-12-28 BorgWarner Inc. Méthode d'assemblage pour une turbomachine
EP2573326A1 (fr) * 2011-09-23 2013-03-27 United Technologies Corporation Agencement de joint d'extrémité d'aube
EP3318719A1 (fr) * 2016-11-07 2018-05-09 United Technologies Corporation Composant de turbomachine revêtu
US10400786B2 (en) 2016-11-07 2019-09-03 United Technologies Corporation Coated turbomachinery component
DE102019116746A1 (de) * 2019-06-20 2020-12-24 Rolls-Royce Deutschland Ltd & Co Kg Rotorbaugruppe und Herstellungsverfahren

Also Published As

Publication number Publication date
CH696854A5 (de) 2007-12-31
US7425115B2 (en) 2008-09-16
JP2006522894A (ja) 2006-10-05
EP1613840A2 (fr) 2006-01-11
US20060062664A1 (en) 2006-03-23
WO2004090290A3 (fr) 2004-11-18

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